Self-retaining shear pin for blind mount location

ABSTRACT

A shear pin connection for use in a difficult to access location has a bolt head to be positioned at an inner end of a bearing. A bushing is received between the bolt and an inner periphery of the bearing. A lock member is positioned between an inner end of the bushing and the bolt head. The lock member is radially expandable, and has a free radially outer dimension that is smaller than an inner dimension of the inner bore. The lock member is expandable to have an expanded radially outer dimension that is greater than the inner dimension of the inner bore. A nut is tightened on the outer end of the bolt. The nut causes the bushing to move relative to the bolt, and causes the lock member to expand radially. A shackle connection for a gas turbine engine and an aircraft are also disclosed.

BACKGROUND OF THE INVENTION

This application relates to a shear pin which can be installed into ablind location.

Gas turbine engines are known, and are typically utilized on aircraftapplications to provide propulsion for the aircraft. This is one exampleof where a shear pin might be utilized.

Typically, a plurality of shackles extend from a static structure on theaircraft, such as the wing, and are attached to the engine case at aplurality of locations. The locations at which the shackle is attachedto the engine case typically include a shear pin that allows movementbetween the shackle and the engine case.

The attachment of the shear pin typically is at a “blind” location, andthus the inner end of the attachment may not be accessible to anassembler.

Proposed shear pin assemblies for use in blind locations have beenunduly complex, and require a large number of parts.

SUMMARY OF THE INVENTION

In a featured embodiment, a shear pin connection for use in a difficultto access location includes a bolt having a bolt head to be positionedat an inner end of a bearing, the bolt extending outwardly through aninner bore in the bearing to an outer end. A bushing is receivedradially outwardly of the bolt, and between the bolt and an innerperiphery of the bearing. A lock member is positioned between an innerend of the bushing and the bolt head. The lock member is radiallyexpandable, and has a free radially outer dimension that is smaller thanan inner dimension of the inner bore. The lock member us expandable tohave an expanded radially outer dimension that is greater than the innerdimension of the inner bore. A nut is tightened on the outer end of thebolt. The nut causes the bushing to move relative to the bolt and causesthe lock member to expand radially.

In another embodiment according to the previous embodiment, the bolt hasa ramped surface for causing the lock member to be ramped radiallyoutwardly as the nut is tightened on the bolt. The bushing and bolt moverelative to each other.

In another embodiment according to any of the previous embodiments, thebushing has an inner ramped surface which is received in contact withthe ramped outer surface of the bolt as the nut is fully tightened onthe bolt.

In another embodiment according to any of the previous embodiments, the

In another embodiment according to any of the previous embodiments, thelock member is an expandable coil spring.

In another embodiment according to any of the previous embodiments, theexpandable coil spring is received on a cylindrical surface on the boltaxially intermediate the inner end of the bushing and bolt head.

In another embodiment according to any of the previous embodiments, theinner end of the bolt will be less accessible than the outer end.

In another featured embodiment, a connection for connecting an aircraftto a gas turbine engine has an outer casing, a plurality of shackleseach mounted to the outer casing through spherical bearings, and atleast one shear pin connection for connecting the outer casing to one ofthe shackles. The shear pin connection includes a bolt having a bolthead to be positioned at an inner end of a bearing. The bolt extendsoutwardly through an inner bore in the bearing to an outer end. Abushing is received radially outwardly of the bolt, and between the boltand an inner periphery of the bearing. A lock member is positionedbetween an inner end of the bushing and bolt head. The lock member isradially expandable, and has a free radially outer dimension that issmaller than an inner dimension of the inner bore. The lock member isexpandable to have an expanded radially outer dimension that is greaterthan the inner dimension of the inner bore. A nut is tightened on theouter end of the bolt causing the bushing to move relative to the bolt,and cause the lock member to expand radially.

In another embodiment according to the previous embodiment, the bolt hasa ramped surface for causing the lock member to be ramped radiallyoutwardly as the nut is tightened on the bolt. The bushing and bolt moverelative to each other.

In another embodiment according to any of the previous embodiments, thebushing has an inner ramped surface that is received in contact with theramped outer surface of the bolt as the nut is fully tightened on thebolt.

In another embodiment according to any of the previous embodiments. thelock member is an expandable coil spring.

In another embodiment according to any of the previous embodiments, theexpandable coil spring is received on a cylindrical surface on the boltaxially intermediate the inner end of the bushing and bolt head.

In another embodiment according to any of the previous embodiments, theinner end of the bolt will be less accessible than the outer end.

In another featured embodiment, an aircraft has an aircraft body, and aplurality of attached shackles. The plurality of shackles are mounted toa gas turbine engine outer casing through spherical bearings, with shearpins connecting the gas turbine engine casing to the shackles. At leastone shear connection includes a bolt having a bolt head to be positionedat an inner end of a bearing. The bolt extends outwardly through aninner bore in the bearing to an outer end. A bushing is receivedradially outwardly of the bolt, and between the bolt and an innerperiphery of the bearing. A lock member is positioned between an innerend of the bushing and bolt head. The lock member is radiallyexpandable, and has a free radially outer dimension that is smaller thanan inner dimension of the inner bore. The lock member is expandable tohave an expanded radially outer dimension that is greater than the innerdimension of the inner bore. A nut is tightened on the outer end of thebolt. The nut causes the bushing to move relative to the bolt, and thelock member to expand radially.

In another embodiment according to the previous embodiment, the bolt hasa ramped surface that causes the lock member to be ramped radiallyoutwardly as the nut is tightened on the bolt. The bushing and bolt moverelative to each other.

In another embodiment according to any of the previous embodiments, thebushing has an inner ramped surface which is received in contact withthe ramped outer surface of the bolt as the nut is fully tightened onthe bolt.

In another embodiment according to any of the previous embodiments, thelock member is an expandable coil spring.

In another embodiment according to any of the previous embodiments, theexpandable coil spring is received on a cylindrical surface on the boltaxially intermediate the inner end of the bushing and bolt head.

In another embodiment according to any of the previous embodiments, theshackles are attached to a wing on the aircraft.

In another embodiment according to any of the previous embodiments, theinner end of the bolt will be less accessible than the outer end.

These and other features may be best understood from the followingdrawings and specification.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1A schematically shows a gas turbine engine.

FIG. 1B schematically shows a mount of a gas turbine engine.

FIG. 2 shows a shear pin system mounting a shackle to an engine casing.

FIG. 3 shows the FIG. 2 system prior to final assembly.

FIG. 4 shows a sub-assembly.

DETAILED DESCRIPTION

FIG. 1A schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude an augmentor section (not shown) among other systems orfeatures. The fan section 22 drives air along a bypass flowpath B whilethe compressor section 24 drives air along a core flowpath C forcompression and communication into the combustor section 26 thenexpansion through the turbine section 28. Although depicted as aturbofan gas turbine engine in the disclosed non-limiting embodiment, itshould be understood that the concepts described herein are not limitedto use with turbofans as the teachings may be applied to other types ofturbine engines including three-spool architectures.

The engine 20 generally includes a low speed spool 30 and a high speedspool 32 mounted for rotation about an engine central longitudinal axisA relative to an engine static structure 36 via several bearing systems38. It should be understood that various bearing systems 38 at variouslocations may alternatively or additionally be provided.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor 44 and a low pressureturbine 46. The inner shaft 40 is connected to the fan 42 through ageared architecture 48 to drive the fan 42 at a lower speed than the lowspeed spool 30. The high speed spool 32 includes an outer shaft 50 thatinterconnects a high pressure compressor 52 and high pressure turbine54. A combustor 56 is arranged between the high pressure compressor 52and the high pressure turbine 54. A mid-turbine frame 57 of the enginestatic structure 36 is arranged generally between the high pressureturbine 54 and the low pressure turbine 46. The mid-turbine frame 57further supports bearing systems 38 in the turbine section 28. The innershaft 40 and the outer shaft 50 are concentric and rotate via bearingsystems 38 about the engine central longitudinal axis A which iscollinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 thenthe high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over the high pressure turbine 54 and lowpressure turbine 46. The mid-turbine frame 57 includes airfoils 59 whichare in the core airflow path. The turbines 46, 54 rotationally drive therespective low speed spool 30 and high speed spool 32 in response to theexpansion.

The engine 20 in one example is a high-bypass geared aircraft engine. Ina further example, the engine 20 bypass ratio is greater than about six(6), with an example embodiment being greater than ten (10), the gearedarchitecture 48 is an epicyclic gear train, such as a planetary gearsystem or other gear system, with a gear reduction ratio of greater thanabout 2.3 and the low pressure turbine 46 has a pressure ratio that isgreater than about 5. In one disclosed embodiment, the engine 20 bypassratio is greater than about ten (10:1), the fan diameter issignificantly larger than that of the low pressure compressor 44, andthe low pressure turbine 46 has a pressure ratio that is greater thanabout 5:1. Low pressure turbine 46 pressure ratio is pressure measuredprior to inlet of low pressure turbine 46 as related to the pressure atthe outlet of the low pressure turbine 46 prior to an exhaust nozzle.The geared architecture 48 may be an epicycle gear train, such as aplanetary gear system or other gear system, with a gear reduction ratioof greater than about 2.5:1. It should be understood, however, that theabove parameters are only exemplary of one embodiment of a gearedarchitecture engine and that the present invention is applicable toother gas turbine engines including direct drive turbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition —typically cruise at about 0.8 Machand about 35,000 feet. The flight condition of 0.8 Mach and 35,000 ft,with the engine at its best fuel consumption—also known as “bucketcruise Thrust Specific Fuel Consumption (‘TSFCT’)”—is the industrystandard parameter of 1bm of fuel being burned divided by 1bf of thrustthe engine produces at that minimum point. “Low fan pressure ratio” isthe pressure ratio across the fan blade alone, without a Fan Exit GuideVane (“FEGV”) system. The low fan pressure ratio as disclosed hereinaccording to one non-limiting embodiment is less than about 1.45. “Lowcorrected fan tip speed” is the actual fan tip speed in ft/sec dividedby an industry standard temperature correction of [(Tambient degR)/518.7)^0.5]. The “Low corrected fan tip speed” as disclosed hereinaccording to one non-limiting embodiment is less than about 1150ft/second.

FIG. 1B shows the attachment of a gas turbine engine 20 to an aircraftstatic structure 18. Aircraft static structure 18 may be a wing, or anyother location on the aircraft which is to attach the engine. As know,shackles 17 and 19 extend from static structure 18 and are connected at80 through shear pins to a casing of the engine 20.

FIG. 2 shows one example shear pin system 80. In system 80, the shackle19 is attached to the engine case 128 through a spherical bearing 124and 126. This will allow adjustment of the orientation of shackle 19relative to the engine case 128. It should be understood that the othershackle 17 may also incorporate similar structure.

A liner (to the left in this Figure) of this system is relativelyinaccessible to an assembler.

A bolt 130 extends through an inner periphery 127 of the inner portion126 of the bearing. As can be appreciated, an outer dimension of thehead 129 of the bolt is slightly smaller than an inner diameter of theinner periphery 127. A bushing 136 is received on the bolt 130. A spring138 extends radially outwardly of the inner diameter of the inner bore127 and provides a stop preventing movement of the bolt 130 to the rightas shown in the Figure. The spring 138 provides a stop member. In oneembodiment, the spring may be formed of a plurality of coils, with afree outer diameter of the spring being roughly equivalent to the outerdiameter of the bolt head 129, and an inner diameter of the spring beingroughly equivalent to an outer diameter of the bolt at a locationforward of a frustoconical surface 131. The spring is preferably aradially expandable item. In one embodiment, a coil spring having aplurality of turns is utilized.

The bolt has a ramped or frustoconical surface 131 received within amating ramp or frustoconical surface 133 in the bushing 136. A nut 134is threaded onto an outer end of the bolt 130. Hexagonal socket 132provides a function which will be described below. The shear pin system80 is assembled from the right-hand side of FIG. 2. The left-hand sideis not accessible, as mentioned.

When initially assembled, the nut 134 is not fully tightened on the bolt130 as shown in FIG. 3. A sub-assembly including the bolt 130, thespring 138 and the bushing 136 are all moved within the inner periphery127 of the spherical bearing. An outer ledge 180 of the bushing 136abuts an outer face of the engine casing 128. As can be appreciated fromFIG. 3, when initially inserted into the bearing 124/126, the bolt 130has not been tightened, and there is a space between the ramped surfaces131 and 133. Further, as can be seen, the spring 138 has a smallerradially outer diameter than it does in the fully assembled position ofFIG. 2. Thus, the spring 138 can also move within the inner periphery127 of the bushing inner portion 126.

FIG. 4 shows the sub-assembly which may be initially moved within theinner portion 126 of the bearing.

Once this sub-assembly is received within the bearing, the nut 134 istightened on the bolt 130. The socket 132 may be utilized to lock thebolt against rotation as this tightening occurs. As the bolt istightened, it is drawn to the right as shown in FIG. 3, and the springis forced radially outwardly along the surface 131, and eventuallydriven further by the bushing 136, which forces it along the surface131. The spring 138 eventually snaps into a cylindrical portion 179formed on the outer periphery of the bolt 130 just forward of the bolthead 129.

The shear pin system 80 thus allows complete assembly from an outerlocation of the connection of the shackle 19 to the engine casing 128.It should, of course, be understood, the same type of connection will beutilized at any number of locations to fully mount the gas turbineengine 20 to the aircraft 18.

Also, the shear pin system 80 may have application for other blindinstallations.

Although an embodiment of this invention has been disclosed, a worker ofordinary skill in this art would recognize that certain modificationswould come within the scope of this invention. For that reason, thefollowing claims should be studied to determine the true scope andcontent of this invention.

The invention claimed is:
 1. A connection for connecting an aircraft toa gas turbine engine comprising: a gas turbine engine having an outercasing; a plurality of shackles each mounted to said outer casingthrough spherical bearings, and at least one shear pin connection forconnecting said outer casing to one of said shackles, said shear pinconnection including a bolt having a bolt head to be positioned at aninner end of a bearing, said bolt extending outwardly through an innerbore in the bearing to an outer end, a bushing received radiallyoutwardly of said bolt, and between said bolt and an inner periphery ofthe bearing, a lock member being positioned between an inner end of saidbushing and said bolt head, and said lock member being radiallyexpandable, and having a free radially outer dimension that is smallerthan an inner dimension of the inner bore, and said lock member beingexpandable to have an expanded radially outer dimension which is greaterthan the inner dimension of the inner bore, and a nut to be tightened onsaid outer end of said bolt, said nut causing said bushing to moverelative to said bolt, and cause said lock member to expand radially. 2.The connection as set forth in claim 1, wherein said bolt has a rampedsurface for causing said lock member to be ramped radially outwardly assaid nut is tightened on said bolt, and said bushing and said bolt moverelative to each other.
 3. The connection as set forth in claim 2,wherein said bushing has an inner ramped surface which is received incontact with said ramped outer surface of said bolt as said nut is fullytightened on said bolt.
 4. The connection as set forth in claim 3,wherein said lock member is an expandable coil spring.
 5. The connectionas set forth in claim 4, wherein said expandable coil spring is receivedon a cylindrical surface on said bolt axially intermediate said innerend of said bushing and said bolt head.
 6. The connection as set forthin claim 1, wherein said inner end of said bolt will be less accessiblethan said outer end.
 7. An aircraft comprising: an aircraft body, and aplurality of shackles attached to said aircraft body, said plurality ofshackles mounted to a gas turbine engine outer casing through sphericalbearings, with shear pins connecting said gas turbine engine casing tosaid shackles, and at least one said shear connection including a bolthaving a bolt head to be positioned at an inner end of a bearing, saidbolt extending outwardly through an inner bore in the bearing to anouter end, a bushing received radially outwardly of said bolt, andbetween said bolt and an inner periphery of the bearing, a lock memberbeing positioned between an inner end of said bushing and said bolthead, and said lock member being radially expandable, and having a freeradially outer dimension that is smaller than an inner dimension of theinner bore, and said lock member being expandable to have an expandedradially outer dimension which is greater than the inner dimension ofthe inner bore, and a nut to be tightened on said outer end of saidbolt, said nut causing said bushing to move relative to said bolt, andcause said lock member to expand radially.
 8. The aircraft as set forthin claim 7, wherein said bolt has a ramped surface for causing said lockmember to be ramped radially outwardly as said nut is tightened on saidbolt, and said bushing and said bolt move relative to each other.
 9. Theaircraft as set forth in claim 8, wherein said bushing has an innerramped surface which is received in contact with said ramped outersurface of said bolt as said nut is fully tightened on said bolt. 10.The aircraft as set forth in claim 9, wherein said lock member is anexpandable coil spring.
 11. The aircraft as set forth in claim 10,wherein said expandable coil spring is received on a cylindrical surfaceon said bolt axially intermediate said inner end of said bushing andsaid bolt head.
 12. The aircraft as set forth in claim 7, wherein saidshackles are attached to a wing on said aircraft.
 13. The aircraft asset forth in claim 7, wherein said inner end of said bolt will be lessaccessible than said outer end.